Pylon mounted tilt rotor

Abstract

A pylon portion includes a first surface that attaches to an upper surface of a spar in a wing, where the pylon portion and a rotor portion protrude aft of the wing. A second surface attaches to a lower surface of the spar in the wing. The pylon portion also includes an intake air vent; a horizontal mounting surface; a rotor controller that is coupled to the horizontal mounting surface; and a heat sink that couples to the horizontal mounting surface and dissipates heat from at least the rotor controller. The rotor portion is moveably coupled to the pylon portion such that one or more rotor blades included in the rotor portion are able to move between: (1) a first position below the wing that is associated with a vertical flight mode and (2) a second position aft of the wing that is associated with a forward flight mode.

What is claimed is: 
     
       1. A system, comprising:
 a pylon portion that includes:
 a first surface that is configured to attach to an upper surface of a spar in a wing, wherein the pylon portion and a rotor portion protrude aft of the wing; 
 a second surface that is configured to attach to a lower surface of the spar in the wing; 
 an intake air vent; 
 a horizontal mounting surface; 
 a rotor controller that is coupled to the horizontal mounting surface; and 
 a heat sink that is coupled to the horizontal mounting surface and that is configured to dissipate heat from at least the rotor controller; and 
 
 the rotor portion, wherein:
 the rotor portion is moveably coupled to the pylon portion such that one or more rotor blades included in the rotor portion are able to move between: (1) a first position below the wing that is associated with a vertical flight mode and (2) a second position aft of the wing that is associated with a forward flight mode. 
 
 
     
     
       2. The system of  claim 1 , wherein the wing includes a forward-swept wing. 
     
     
       3. The system of  claim 1 , wherein the wing includes a tapered wing. 
     
     
       4. The system of  claim 1 , wherein:
 the wing includes a forward spar and an aft spar; and 
 the first surface and the second surface of the pylon portion are configured to attach, respectively, to the upper surface and the lower surface of the aft spar in the wing. 
 
     
     
       5. The system of  claim 1 , wherein the intake air vent is disposed on a bottom surface of the pylon portion. 
     
     
       6. The system of  claim 1 , wherein the heat sink in the pylon portion is associated with a cooler typical temperature than a rotor in the rotor portion such that heat sink heated air that passes over the heat sink is able to subsequently cool the rotor in the rotor portion. 
     
     
       7. The system of  claim 1 , wherein in an event the rotor portion is in the second position that is associated with the forward flight mode, the one or more rotor blades are within a range of 500-650 mm from the wing. 
     
     
       8. A method, comprising:
 providing a pylon portion that includes:
 a first surface that is configured to attach to an upper surface of a spar in a wing, wherein the pylon portion and a rotor portion protrude aft of the wing; 
 a second surface that is configured to attach to a lower surface of the spar in the wing; 
 an intake air vent; 
 a horizontal mounting surface; 
 a rotor controller that is coupled to the horizontal mounting surface; and 
 a heat sink that is coupled to the horizontal mounting surface and that is configured to dissipate heat from at least the rotor controller; and 
 
 providing the rotor portion, wherein:
 the rotor portion is moveably coupled to the pylon portion such that one or more rotor blades included in the rotor portion are able to move between: (1) a first position below the wing that is associated with a vertical flight mode and (2) a second position aft of the wing that is associated with a forward flight mode. 
 
 
     
     
       9. The method of  claim 8 , wherein the wing includes a forward-swept wing. 
     
     
       10. The method of  claim 8 , wherein the wing includes a tapered wing. 
     
     
       11. The method of  claim 8 , wherein:
 the wing includes a forward spar and an aft spar; and 
 the first surface and the second surface of the pylon portion are configured to attach, respectively, to the upper surface and the lower surface of the aft spar in the wing. 
 
     
     
       12. The method of  claim 8 , wherein the intake air vent is disposed on a bottom surface of the pylon portion. 
     
     
       13. The method of  claim 8 , wherein the heat sink in the pylon portion is associated with a cooler typical temperature than a rotor in the rotor portion such that heat sink heated air that passes over the heat sink is able to subsequently cool the rotor in the rotor portion. 
     
     
       14. The method of  claim 8 , wherein in an event the rotor portion is in the second position that is associated with the forward flight mode, the one or more rotor blades are within a range of 500-650 mm from the wing.